Systems and methods for wide set retracting landing gear of a cargo aircraft. One embodiment is an aircraft that includes a fuselage including a nose, and a pair of main landing gears comprising a pair of main posts disposed across the fuselage, each main post having a main wheel and configured to pivot forward toward the nose to retract the main wheel. The aircraft also includes a pair of nose landing gears comprising a pair of nose posts disposed across the fuselage, each nose post having a nose wheel and configured to pivot inboard to retract the nose wheel.

A nose landing gear assembly includes an oleo strut, a forward brace including a forward brace first end and a forward brace second end. The forward brace first end is pivotably coupled to the nose gear bay of a high wing aircraft about a first pivot axis. The assembly also includes an aft brace including an aft brace first end and an aft brace second end. The aft brace first end is pivotably coupled to the nose gear bay about a second pivot axis, and the aft brace second end is pivotably coupled to the oleo strut. An actuator includes an actuator first end and an actuator second end. The actuator second end is coupled to the nose gear bay and the actuator first end coupled to the forward brace. The actuator is configured to move the nose landing gear assembly between a retracted position and an extended position.

A nose landing gear assembly includes an oleo strut, a forward brace including a forward brace first end and a forward brace second end. The forward brace first end is pivotably coupled to the nose gear bay of a high wing aircraft about a first pivot axis. The assembly also includes an aft brace including an aft brace first end and an aft brace second end. The aft brace first end is pivotably coupled to the nose gear bay about a second pivot axis, and the aft brace second end is pivotably coupled to the oleo strut. An actuator includes an actuator first end and an actuator second end. The actuator second end is coupled to the nose gear bay and the actuator first end coupled to the forward brace. The actuator is configured to move the nose landing gear assembly between a retracted position and an extended position.

A truck beam for an aircraft landing gear assembly is provided. The truck beam includes an elongate hub having first and second ends. The hub is rotatably mountable a shock strut of the landing gear assembly. A first leg extends radially in a first direction from the first end of the hub. The first leg has an inner side facing the second end of the hub and is configured to have a first wheel rotatably mounted to the inner side about a first wheel axis. A second leg extends radially in a second direction from the second end of the hub and has an inner side facing the first end of the hub. The second leg is configured to have a second wheel rotatably mounted to the inner side of the second leg about a second wheel axis.

A truck beam for an aircraft landing gear assembly is provided. The truck beam includes an elongate hub having first and second ends. The hub is rotatably mountable a shock strut of the landing gear assembly. A first leg extends radially in a first direction from the first end of the hub. The first leg has an inner side facing the second end of the hub and is configured to have a first wheel rotatably mounted to the inner side about a first wheel axis. A second leg extends radially in a second direction from the second end of the hub and has an inner side facing the first end of the hub. The second leg is configured to have a second wheel rotatably mounted to the inner side of the second leg about a second wheel axis.

An aircraft subassembly comprises a fuselage structure, comprising a first side and a second side. The aircraft subassembly further comprises a main-landing-gear system, having a single pair of wheels. The main-landing-gear system additionally comprises a sponson, connected to and extending outward from the fuselage structure. The sponson comprises a central portion and a first main-landing-gear door that is moveable relative to the central portion between, inclusively, a closed position and an open position. The sponson further comprises a second main-landing-gear door that is moveable relative to the central portion between, inclusively, a closed position and an open position. The main-landing-gear system further comprises a first main-landing-gear assembly, connected to the first wheel and a second main-landing-gear assembly, connected to the second wheel.

An aircraft subassembly comprises a fuselage structure, comprising a first side and a second side. The aircraft subassembly further comprises a main-landing-gear system, having a single pair of wheels. The main-landing-gear system additionally comprises a sponson, connected to and extending outward from the fuselage structure. The sponson comprises a central portion and a first main-landing-gear door that is moveable relative to the central portion between, inclusively, a closed position and an open position. The sponson further comprises a second main-landing-gear door that is moveable relative to the central portion between, inclusively, a closed position and an open position. The main-landing-gear system further comprises a first main-landing-gear assembly, connected to the first wheel and a second main-landing-gear assembly, connected to the second wheel.

A folding trailing arm landing gear assembly having a main fitting configured to couple to a hinge positioned at a proximal end; a swing arm rotatably coupled at a proximal end to a distal end of the main fitting; a shock coupled at a distal end to a distal end of the swing arm; a bellcrank coupled at a distal end to a proximal end of the shock, and coupled at a proximal end to the main fitting; and a wheel coupled to the swing arm.

A folding trailing arm landing gear assembly having a main fitting configured to couple to a hinge positioned at a proximal end; a swing arm rotatably coupled at a proximal end to a distal end of the main fitting; a shock coupled at a distal end to a distal end of the swing arm; a bellcrank coupled at a distal end to a proximal end of the shock, and coupled at a proximal end to the main fitting; and a wheel coupled to the swing arm.

An aircraft subassembly comprises a fuselage structure, comprising a first side and a second side. The aircraft subassembly further comprises a main-landing-gear system, having a single pair of wheels. The main-landing-gear system additionally comprises a sponson, connected to and extending outward from the fuselage structure. The sponson comprises a central portion and a first main-landing-gear door that is moveable relative to the central portion between, inclusively, a closed position and an open position. The sponson further comprises a second main-landing-gear door that is moveable relative to the central portion between, inclusively, a closed position and an open position. The main-landing-gear system further comprises a first main-landing-gear assembly, connected to the first wheel and a second main-landing-gear assembly, connected to the second wheel.